Projectile launching device



Jan. 9, 1962 E. E. FORBES, JR

PROJECTILE LAUNCHING DEVICE 2 Sheets-Sheet 1 Filed Oct. 29, 1958 INVENTOR ATTORNEYIS Jan. 9, 1962 E. E. FORBES, JR 3,015,991

PROJECTILE LAUNCHING DEVICE Filed Oct. 29. 1958 2 Sheets-Sheet 2 I N VE N TOR EV/V5575. K'OPEEM ATTORNEY5 Patented Jan. 9, 1962 3,015,991 PROJECTILE LAUNCHING DEVICE Ernest E. Forbes, Jr., 2600 3rd Ave. 8., Birmingham, Ala. Filed Oct. 29, 1958, Ser. No. 770,397 4 Claims. (Cl. 89-1.7)

This invention relates to a projectile launching device and more particularly to a carriage member adapted to be detachably secured to a rocket projectile to permit firing from a smooth bore gun barrel.

It is well known that a projectile may be stabilized in flight by imparting a rapid spinning motion thereto. To accomplish this desired result, it is conventional to provide the launching barrel with a series of spiral grooves known as riflings. A properly designed projectile, having a rapid spinning motion imparted thereto by launching from a rifled barrel, is aerodynamically stable and will remain on its directed course, thus providing the requisite accuracy.

The rifled barrels heretofore used have been expensive because of the cost of the riflings, and the heavy construction and recoil mechanism required to absorb the shock produced by forces of launching. Furthermore, since the projectile must be of the same size as the interior diameter of the riflings in order for the riflings to be operative, it is necessary to provide a difierent barrel for each size projectile to be launched.

Accordingly, it is the object of this invention to provide a launching device which overcomes the above-mentioneddifiiculties.

Another object of this invention i to provide a projectile carriage capable of imparting the required spin to a projectile without the use of rifled barrels.

Another object of the invention is to provide a projectile carriage which is detachably secured to a projectile and which utilizes the exhaust gases of the projectile to impart the required spin to the projectile.

A further object of this invention is to provide a detachable launching carriage which enables clilferent size projectiles to be launched from a standard size barrel.

According to a preferred embodiment of the invention, these objects are accomplished by providing a carriage assembly comprising a pair of spaced concentric cylindrical tubes having located therebetween a series of curved blades. Positioned within the inner tube is a frusto-conical frame for holding a projectile therein.

The projectile and carriage assembly is adapted to fit in a gun barrel having a smooth bore, and when the projectile is fired the exhaust gases are directed through the space between the inner and outer cylindrical tubes. In passing through this space, the exhaust gases impinge against the curved blades and thereby cause a spinning motion to be imparted to the projectile and carriage assembly.

This preferred embodiment of the invention is illustrated in the accompanying drawings in which:

FIG. 1 is a partial cross-section of a projectile suitable for use with the carriage of the instant invention;

FIG. 2 is a cross-section of the carriage assembly;

FIG. 3 is an end view of the carriage assembly;

FIG. 4 is a cross-section taken along line 4-4 of FIG. 3;

FIG. 5 is a cross-section showing the projectile and launching carriage in place in the barrel of a gun; and

FIG. 6 is an end view of the assembly of FIG. 5.

For the purposes of this description, it will be assumed that the projectile described is a rocket, although it will be understood by those skilled in the art that the invention is applicable to other types of projectiles.

Referring now to FIG. 1, a projectile, generally designated by the numeral 1, is shown to be of tear-drop shape. This particular shape has been selected for three reasons. First, this shape afitords excellent wind resistance characteristics when in flight; second, the rearwardly tapering body portion enables the carriage member to drop free of the rocket after firing; and third, the enlarged burning surface will produce a greater jet force as the rocket increases its velocity, thereby increasing the ultimate velocity of the projectile.

The rocket 1 comprises a head member 3 having a hollow portion 5 therein which is adapted to contain an explosive charge, if desired. The base of the head 3 is provided with screw threads 7 by means of which the head may be fastened to the frusto-conical body member 9. The lower end of body member 9 has an aperture 11 located therein. The body member 9 is adapted to contain the propelling charge to power the rocket, and the exhaust gases liberated by such charge are exhausted through aperture 11.

The overall construction of the launching carriage may be seen from FIG. 2, which is a cross-section thereof. The carriage comprises a pair of concentric tubular members 13 and 1-5, which are mounted in spaced relationship by means of a plurality of curved fin members 17. These fin members 17 serve the dual purpose of securing the tubes 13, 15 in spaced relation and also providing the means for imparting rotation to the launching carriage when the rocket is fired. The fins may be secured in the desired position by any conventional means such as Weldmg.

FIG. 4 is a cross'section view taken through one of the fin members 17 and shows the angular positioning of the members. It will be appreciated that the number of these fins and the particular angle at which they are positioned may be varied in accordance with the amount of spin required.

Fixedly mounted within the interior of tube 13 is a frusto-conical sleeve member 19, the upper end 21 of which is secured to the tubular member 13 by any suitable means, such as spot welding. The lower end of sleeve 19 is spaced from tubular member 13 by means of an annular disc member 23 which seals ofi the space therebetween. The tubular members 13 and 15, fins 17, and sleeve 19 may be made of any suitable material, but are preferably made of steel because of its strength and ability to withstand heat.

Located within sleeve 19 is a second sleeve 25 made of asbestos material. The function of sleeve 25 is to insulate the rocket from the heat or" the exhaust gases passing upward through the annular space 27 between tubular members 13 and 15. It will be seen from the drawings that the tube 13 extends the full length of the rocket, thereby keeping the hot exhaust gases from contacting the rocket head 3. The outside of tubular member 15 is provided with bronze graphite bearing rings 29 whose purpose is to facilitate the passage of the carriage through the bore of the barrel by providing the necessary lubrication.

Referring now to FIGS. 5 and 6, the carriage and rocket assembly is shown in place in a barrel 31. Barrel 31 is constructed of stainless steel, and is of the same thickness throughout its length. Since the novel means for utilizing the rocket exhaust gases prevents any sudden explosive pressures to develop, the thickness of the barrel need not be as great as a conventional projectile firing barrel. This permits the use of a longer, lighter weight barrel.

Located about the outer periphery of barrel 31 and fastened thereto by suitable means such as welding, are a plurality of welded strips 33 which provide the barrel with the requisite rigidity and also serve to dissipate the heat generated within the barrel.

Located in the lower end of the barrel 31 is an exhaust gas diverting element 35 having an annular depression 37 located in the top surface thereof, leaving a central point or spire 39 in the center. The exhaust gases from rocket 1 are redirected by means of element 35 so as to be channeled through space 27 of the carriage where they impinge on fins 17 and produce rotation of the carriage assembly. It will be understood that the size of space 27 may be varied, when necessary, to control the effective exhausting of the gases from the barrel 31.

The rapid exhaust of gases through the carriage assembly will cause a reduced pressure section to exist in front of the rocket 1. This action assists in the rapid acceleration of the rocket, and enables the rocket to attain velocities not heretofore possible.

To facilitate handling of the rocket and carriage assembly as a unit, the rocket may be secured to the carriage by means of plastic straps (not shown). When the rocket is fired, the heat from the exhaust gases will melt the straps thus allowing the carriage to fall free of the rocket upon leaving gun barrel 31.

By employing a standard size outer tube 15 and varying the size of the inner tube 13 and sleeve 19, it is possible to use a single barrel for firing a number of different sizes of rockets.

It will be seen from the foregoing description that a launching device has been provided which enables the accurate firing of projectiles without the use of rifled barrels. Rockets launched from carriages constructed in accordance with the instant invention require no guiding fins, since the rotation imparted by the spinning carriage stabilizes the projectile and eliminates the need for fins. Furthermore, a rocket thus launched will achieve greater speed since the thrust produced by the exhausting gases is supplemented by the force of the redirected gases acting upon the carriage fins.

While the invention has been described in one embodiment, it will be recognized that variations and changes may be made therein Without departing from the invention as set forth in the claims.

I claim:

1. A device for launching a projectile comprising a rocket; a smooth bore barrel closed at one end; a rocket launching carriage within said barrel including a first cylindrical tube, a second-cylindrical tube mounted within said first tube coaxially therewith to define an annular space between said tubes, fin members disposed along the longitudinal axis at an angle thereto and secured to both of said tubes to position said tubes in a spaced relationship, and means mounted within said second tube to support said rocket; said launching being facilitated by the forward motion of the exhaust gases from said rocket which are deflected from said closed end and against said fin members when said rocket is supported in said carriage and said carriage is located in said smooth bore barrel.

2. A launching device for use with a smooth bore barrel closed at one end comprising a rocket, a first cylindrical tube, a second cylindrical tube mounted within said first tube to define an air space therebetween, curved fin members secured to both of said tubes and located therebetween to mount said tubes in spaced relationship, and a frusto-conical sleeve member mounted within said second tube to support said rocket, said launching being facilitated by the exhause gases from said rocket being deflected from said closed end and impinging against said curved fin members when said device is located in said smooth bore barrel.

3. The combination according to claim 2 wherein a heat insulating sleeve is located within said frusto-conical sleeve member to insulate the rocket from extreme temperatures.

4. The combination according to claim 2 wherein a plurality of bearing rings are mounted on the outer surface of said first tube to facilitate the passage of the device through the barrel.

References Cited in the file of this patent UNITED STATES PATENTS 1,341,844 Dougan June 1, 1920 1,368,057 Rooney Feb. 8, 1921 1,611,431 Froelich Dec. 21, 1926 2,247,563 Spalding July 1, 1941 2,383,053 Fanger et al. Aug. 21, 1945 2,559,955 Hartwell July 10, 1951 2,766,691 Ramey Oct. 16, 1956 2,788,744 Donner Apr. 16, 1957 2,802,399 Little Aug. 13, 1957 2,901,973 Donner Sept. 1, 1959 

